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A novel centrifugal diffuser test deviceA large scale (2 in.-wide test vanes at 50-in. inlet diameter), low speed (100-200 ft/sec) steady flow radial cascade wind tunnel for diffuser studies was designed, built and tested. The apparatus was shown to provide flow angles (from radial) in the range of 58-72 deg with suitable spanwise profiles. The novel flow angle control mechanism was shown to work, but measured flow angles were somewhat smaller than expected. The mechanism for controlling case-wall boundary layer profile did not behave as predicted. Attempts to predict the generated flow both analytically and with computational codes are compared with initial measurements. The low speed apparatus will be used to obtain detailed data for diffuser design and analysis code verification, and to provide experience toward the design of a high speed device.
Document ID
19860039189
Document Type
Conference Paper
Authors
Shreeve, R. P. (Naval Postgraduate School Monterey, CA, United States)
Schulz, H. D. (Naval Postgraduate School Monterey, CA, United States)
Erwin, J. R. (U.S. Naval Postgraduate School Monterey, CA, United States)
Schumann, L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
September 1, 1985
Subject Category
AERODYNAMICS
Report/Patent Number
ASME PAPER 85-IGT-135
Distribution Limits
Public
Copyright
Other